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111. 发明申请

US20130025258A1 GEARED TURBOFAN BEARING ARRANGEMENT 有权
标题翻译：齿轮式涡轮轴承安装
公开(公告)号：US20130025258A1
公开(公告)日：2013-01-31
申请号：US13193790
申请日：2011-07-29
申请人： Brian D. Merry , Gabriel L. Suciu
发明人： Brian D. Merry , Gabriel L. Suciu
IPC分类号： F02K3/02
CPC分类号： F02C7/06 , F01D25/16 , F05D2240/50
摘要： A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.
摘要翻译：齿轮涡轮风扇燃气涡轮发动机包括风扇部分和芯部分。核心部分包括压缩机部分，燃烧器部分和涡轮部分。风扇部分包括齿轮箱和风扇。低阀芯包括在涡轮机部分内的低涡轮机和与用于驱动风扇的齿轮箱的前向连接。支撑支架用于通过前滚子轴承在最向前的位置绕轴线旋转，并在后部位置由推力轴承旋转。

112. 发明授权

US08328133B2 Mounting system for a gas turbine engine 有权
标题翻译：燃气轮机的安装系统
公开(公告)号：US08328133B2
公开(公告)日：2012-12-11
申请号：US13414763
申请日：2012-03-08
申请人： Gabriel L. Suciu , Brian D. Merry , David W. J. Franklin , Christopher M. Dye
发明人： Gabriel L. Suciu , Brian D. Merry , David W. J. Franklin , Christopher M. Dye
IPC分类号： B64D27/02
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268
摘要： A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine.
摘要翻译：用于燃气涡轮发动机的安装系统包括安装连杆组件和大致横向于安装连杆组件定位的切向连杆。安装联动装置至少起反推力。切向连杆至少响应燃气涡轮发动机的垂直载荷，侧向载荷和扭矩载荷。

113. 发明申请

US20120301285A1 CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE TURBINE 有权
标题翻译：用于气体涡轮发动机涡轮机的陶瓷基体复合材料结构
公开(公告)号：US20120301285A1
公开(公告)日：2012-11-29
申请号：US13116053
申请日：2011-05-26
申请人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry , Christopher M. Dye
发明人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry , Christopher M. Dye
IPC分类号： F01D9/04
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
摘要： A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.
摘要翻译：一种用于燃气涡轮发动机的叶片结构，其包括集成在CMC外环和CMC内环之间的多个CMC翼型部分。

114. 发明申请

US20120301275A1 INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR MODULE FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的集成陶瓷基体复合转子模块
公开(公告)号：US20120301275A1
公开(公告)日：2012-11-29
申请号：US13116129
申请日：2011-05-26
申请人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
发明人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
IPC分类号： F01D5/02 , B23P15/04
CPC分类号： F01D5/34 , C04B37/001 , C04B2237/38 , C04B2237/76 , C04B2237/84 , F01D5/282 , F01D5/284 , F01D11/001 , F05D2300/6033 , Y10T29/4932
摘要： A rotor module for a gas turbine engine includes a multiple of CMC airfoil rows which extend from a common CMC drum.
摘要翻译：用于燃气涡轮发动机的转子模块包括从公共CMC鼓延伸的多个CMC翼型排。

115. 发明授权

US08277174B2 Gas turbine engine compressor arrangement 有权
标题翻译：燃气涡轮发动机压缩机布置
公开(公告)号：US08277174B2
公开(公告)日：2012-10-02
申请号：US13418457
申请日：2012-03-13
申请人： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
发明人： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC分类号： F01D25/28
CPC分类号： F02K3/025 , F02C3/107 , F02C7/00 , F02K3/06 , F05D2260/4031
摘要： A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
摘要翻译：燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。压缩机部分包括低压压缩机部分和高压压缩机部分。涡轮部分构造成驱动压缩机部分和齿轮装置。由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约而高压压缩机部分的压力比为约7至约15。

116. 发明申请

US20120216548A1 SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES 有权
标题翻译：涉及气体涡轮发动机的多个扭矩模块的系统和方法
公开(公告)号：US20120216548A1
公开(公告)日：2012-08-30
申请号：US13466745
申请日：2012-05-08
申请人： Michael E. McCune , Brian D. Merry , Gabriel L. Suciu
发明人： Michael E. McCune , Brian D. Merry , Gabriel L. Suciu
IPC分类号： F02C7/00
CPC分类号： F01D21/02 , F01D21/04 , F01D25/16 , F02C3/107 , F02C7/36 , F05D2270/091
摘要： Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative method for reducing overspeed potential of a turbine of a gas turbine engine includes: providing a first load to the turbine via a first torque path; providing a second load to the turbine via a second torque path; and operating the turbine such that: mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path; and mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path.
摘要翻译：提供了涉及燃气涡轮发动机的多个扭矩路径的系统和方法。在这方面，用于降低燃气涡轮发动机的涡轮机的超速电位的代表性方法包括：经由第一扭矩路径向涡轮机提供第一负载; 经由第二扭矩路径向所述涡轮机提供第二负载; 并且操作所述涡轮机，使得限定所述第一扭矩路径的至少一部分的部件的机械故障不阻止所述第二负载经由所述第二扭矩路径施加到所述涡轮机; 并且限定第二扭矩路径的部件的机械故障不阻止第一负载经由第一扭矩路径施加到涡轮机。

117. 发明授权

US08167551B2 Gas turbine engine with 2.5 bleed duct core case section 有权
标题翻译：燃气涡轮发动机带有2.5排放管芯芯部分
公开(公告)号：US08167551B2
公开(公告)日：2012-05-01
申请号：US12411452
申请日：2009-03-26
申请人： Brian D. Merry , Gabriel L. Suciu
发明人： Brian D. Merry , Gabriel L. Suciu
IPC分类号： F01D1/02
CPC分类号： F02K3/06 , F02C9/18 , F04D29/522 , F05D2260/606
摘要： A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a rear structural wall.
摘要翻译：用于燃气涡轮发动机的核心壳部分是由后结构壁部分限定的多个离散的径向延伸的2.5排放管。

118. 发明授权

US08162605B2 Gas turbine engine case 有权
标题翻译：燃气涡轮发动机外壳
公开(公告)号：US08162605B2
公开(公告)日：2012-04-24
申请号：US12013617
申请日：2008-01-14
申请人： Ioannis Alvanos , Gabriel L. Suciu , Brian D. Merry
发明人： Ioannis Alvanos , Gabriel L. Suciu , Brian D. Merry
IPC分类号： F01D25/28
CPC分类号： F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/60 , Y02T50/671 , Y10T29/49826
摘要： A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.
摘要翻译：燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。

119. 发明授权

US08118251B2 Mounting system for a gas turbine engine 有权
标题翻译：燃气轮机的安装系统
公开(公告)号：US08118251B2
公开(公告)日：2012-02-21
申请号：US12016337
申请日：2008-01-18
申请人： Gabriel L. Suciu , Brian D. Merry , Jon A. Marx , Christopher M. Dye
发明人： Gabriel L. Suciu , Brian D. Merry , Jon A. Marx , Christopher M. Dye
IPC分类号： B64D27/00 , F02C7/20
CPC分类号： B64D27/18 , B64D27/26 , F02C7/20
摘要： A mounting system for a gas turbine engine includes a thrust ring and a linkage assembly. The linkage assembly is at least partially received by the thrust ring. The linkage assembly reacts at least a side load and a thrust load communicated from the thrust ring.
摘要翻译：用于燃气涡轮发动机的安装系统包括推力环和连杆组件。连杆组件至少部分地被推力环接收。连杆组件至少反作用于从止推环传递的侧向载荷和推力载荷。

120. 发明授权

US07955046B2 Gas turbine engine front architecture modularity 有权
标题翻译：燃气轮机发动机前架构模块化
公开(公告)号：US07955046B2
公开(公告)日：2011-06-07
申请号：US11860719
申请日：2007-09-25
申请人： Michael E. McCune , Brian D. Merry , Gabriel L. Suciu
发明人： Michael E. McCune , Brian D. Merry , Gabriel L. Suciu
IPC分类号： F01D25/24
CPC分类号： F02C7/36 , F02C7/04 , F02K3/06 , F05D2230/60
摘要： A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.
摘要翻译：公开了一种燃气涡轮发动机，其包括具有压缩机部分的阀芯。入口壳体在压缩机部分的轴向上游设置。齿轮箱固定在入口箱上。齿轮箱连接线轴和风扇。密封组件布置在入口壳体和齿轮箱之间以提供密封的轴承隔室。入口箱，齿轮箱和密封组件提供一个模块。紧固元件将模块可拆卸地固定到线轴上。燃气涡轮发动机可以通过将紧固元件与发动机芯断开来进行维修。齿轮箱和进气口箱可以作为模块从发动机内芯上拆下，而不必拆卸变速箱。

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